MW级超临界二氧化碳向心涡轮设计及分析

Aerodynamic Design and Analysis of a MWe Supercritical Carbon Oxide Radial-Inflow Turbine

本文以某MW级超临界二氧化碳(S-CO_(2))向心涡轮为研究对象,对S-CO_(2)向心涡轮的设计体系展开进一步探索,并利用一维分析方法和三维数值模拟方法对其进行气动分析。文中先介绍了本课题组已经开发完成的针对向心涡轮喷嘴和转子叶轮的一维气动优化设计方法,然后补充向心涡轮进气蜗壳的设计方法,最后利用三维CFD方法对设计方案的进气蜗壳、喷嘴和转子叶轮进行耦合计算,并根据三维计算结果对静子部件的一维模型进行了校核。结果显示,开发的优化设计方法有效,优化后涡轮在全部工况下效率和通流能力都有所提高;本文设计的MW级向心涡轮设计点效率88.45%,满足设计要求;本文设计的向心涡轮进气蜗壳气动性能良好,而且其内部流场基本不随运行工况的变化而变化;该方案静子部分的总压损失系数约为0.133。

In this paper,a MWe supercritical carbon dioxide(S-CO_(2))radial-inflow turbine is taken as the research object.The design system of S-CO_(2) radial-inflow turbine is further explored,and aerodynamic analysis is carried out using one-dimensional analysis method and three-dimensional numerical simulation method.Firstly,this paper introduced the one-dimensional aerodynamic optimization design method for the radial-inflow turbine nozzle and rotor impeller that has been developed by our group.Then,the design method of the radial-inflow turbine inlet volute is supplemented.Finally,the coupling calculation for the inlet volute,nozzle and rotor impeller of the S-CO_(2) radialinflow turbine is carried out by the three-dimensional CFD method.The loss model of the stator component is checked based on the simulation results.The results show that the optimized design method is effective,and the efficiency and flow capacity of the turbine are improved under all working conditions.The efficiency of the designed MWe S-CO_(2) radial-inflow turbine is 88.45%at design point,which meets the design requirements;the aerodynamic performance of the inlet volute designed is good,and its internal flow field does not change with the change of operating conditions;the total pressure loss coefficient of stator component is about 0.133.